Mid-Continent Instruments MD41, MD41-1498W, MD41-1494W, MD41-1484W, MD41-1488W Installation Manual And Operating Instructions

INSTALLATION MANUAL AND

OPERATING INSTRUCTIONS

MD41-( ) Series GPS Annunciation Unit

For Garmin GNS 430/430W/530/530W VHF

Communication and Navigation Management System

MD41-1484W 14VDC Horizontal Mount
MD41-1488W 28VDC Horizontal Mount
MD41-1494W 14VDC Vertical Mount
MD41-1498W 28VDC Vertical Mount

MID-CONTINENT INST. CO., INC MANUAL NUMBER 9016478

Revision History

ECO Rev. Date Detail

N/R 01/19/07 Initial release.
A 02/15/07 J1 connector was 9016475, now 9016479.

4828

B 03/12/07 Corrected section 4.1 to show proper pins,

corrected mating connector rear view.

C 4/24/07 Correct connector schematic pinout in section

1.2.5. Add –1494W and –1498W versions.

REV. C 2 April 24, 2007

TABLE OF CONTENTS

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

1.2 SPECIFICATIONS, TECHNICAL

1.2.1 PHYSICAL CHARACTERISTICS

1.2.2 ENVIRONMENTAL CHARACTERISTICS

1.2.3 SPECIFICATIONS, ELECTRICAL

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

1.2.4.1 CONTROLS

1.2.4.2 ANNUNCIATIONS

1.2.5 INTERFACE

1.2.6 EQUIPMENT LIMITATIONS

1.2.7 MAJOR COMPONENTS

SECTION 2 INSTALLATION CONSIDERATIONS

2.1 COOLING

2.2 EQUIPMENT LOCATION

2.3 ROUTING OF CABLES

SECTION 3 INSTALLATION PROCEDURE

3.1 GENERAL INFORMATION

3.2 UNPACKING AND INSPECTING

3.3 MOUNTING THE MD41-( )

3.4 INSTALLATION LIMITATIONS

SECTION 4 POST INSTALLATION CHECKOUT

4.1 PRE-INSTALLATION TEST

4.2 OPERATING INSTRUCTIONS

FIGURES LIST OF ILLUSTRATIONS

3.1 SCHEMATIC PINOUT, 15 PIN HIGH DENSITY D-SUB

3.2 OUTLINE DRAWING

3.3 INSTRUMENT PANEL MOUNTING

3.4 WIRING DIAGRAM, MD41-1484W/1488W/1494W/1498W
APPENDIX RTCA DO-160C ENVIRONMENTAL QUALIFICATION FORM

REV. C 3 April 24, 2007

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

The MD41-( ) is a compact, self-contained GPS Annunciation unit. This unit
displays status annunciation received from the Garmin GNS 430/430W/530/530W
series GPS navigation management systems.

Features include dual 20,000 hour lamps used for all annunciations along with
automatic photocell dimming. An external annunciation dimming adjustment is
provided for balancing low-level light conditions.

1.2 TECHNICAL SPECIFICATIONS

1.2.1 PHYSICAL CHARACTERISTICS

Mounting: Front mount, panel
Width: 2.45 inches
Height: 0.75 inches
Depth: 2.60 inches (max)
Weight: 0.2 pounds

1.2.2 ENVIRONMENTAL CHARACTERISTICS

TSO Compliance: TSO C129
Applicable Documents: RTCA DO-160C, DO-208

Operating Temperature Range: -55°C to +70°C
Humidity: 95% Non-Condensing
Altitude Range: 0 to 55,000 ft.
Vibration: RTCA DO-160C, Cat. M and N
Operational Shock: Rigid Mounting, 6G Operational
15 G Crash Safety

REV. C 4 April 24, 2007

1.2.3 ELECTRICAL SPECIFICATIONS

Design All Solid State
MD41-1484W (14VDC) 0.30 Amps
MD41-1488W (28VDC) 0.25 Amps
MD41-1494W (14VDC) 0.30 Amps
MD41-1498W (28VDC) 0.25 Amps

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

1.2.4.1 ANNUNCIATIONS

VLOC NAV or ILS information presented on the HSI or CDI
GPS GPS information presented on the HSI or CDI
MSG ON indicates message(s) active.
WPT ON indicates reaching the arrival waypoint.
TERM ON indicates aircraft is within 30 miles of departure or
arrival airport

APR ON indicates the approach is active.
INTG ON indicates GPS receiver detected a position error
or is unable to calculate the integrity of the position

1.2.5 INTERFACE

INTG annunciation Requires a logic low to annunciate

J1 Pin 1

WPT annunciation Requires a logic low to annunciate

J1 Pin 2 when in VOR/ILS mode

MSG annunciation Requires a logic low to annunciate

J1 Pin 3

TERM annunciation Requires a logic low to annunciate

J1 Pin 4

APR annunciation Requires a logic low to annunciate

J1 Pin 6

VLOC annunciation Receives ground from GNS 430/530

J1 Pin 7

GPS annunciation Receives ground from GNS 430/530

J1 Pin 8 when in GPS mode.

Lamp Test Receives ground from remote test switch

J1 Pin 10 to light all annunciations (optional connection)

J1 Pin 15 Ground

REV. C 5 April 24, 2007

1.2.6 EQUIPMENT LIMITATIONS

The MD41-( ) series control units contain specific dash numbers to be used with
various GPS receivers or Navigation Management Systems. The installer must match
the correct controller part number with the system being installed.

The conditions and tests required for TSO approval of this article are minimum
performance standards. It is the responsibility of those desiring to install this article
either on or within a specific type or class of aircraft to determine that the aircraft
installation conditions are within the TSO standards. The article may be installed
only if further evaluation by the applicant documents an acceptable installation and
is approved by the Administrator.

The MD41-1484W/1488W/1494W/1498W are TSO certified and approved for use
with the Garmin GNS 430/430W/530/530W system. This includes the (A), (W) and
TAWS system versions of the Garmin equipment. Any attempts to install the listed
units in an installation other than the GNS 430/530 system is prohibited.

This will void the TSO.
NOTE: If the MD41-( ) is disconnected or removed from the aircraft, it will not

affect the operation of the GNS 430/430W/530/530W.

1.2.7 MAJOR COMPONENTS

This system is comprised of one major component, the MD41­1484W/1488W/1494W/1498W GPS Annunciation Control Units.

REV. C 6 April 24, 2007

SECTION 2: INSTALLATION CONSIDERATIONS

2.1 COOLING

No direct cooling is required. As with any electronic equipment, overall reliability may
be increased if the MD41-( ) is not located near any high heat source or crowded next
to other equipment. Means of providing a gentle airflow will be a plus.

2.2 EQUIPMENT LOCATION

The MD41-( ) must be mounted as close to the pilot’s field of view as possible. The
preferable location is near the HSI/CDI that will be displaying the GPS/VLOC
information. The unit depth, with connector attached, must also be taken into
consideration. Note: Unlike previous versions of the MD41 Annunciation Control Units
(ACU), the transfer relays are not required since the GNS 430/530 handles all
switching between GPS, VOR and ILS. This has allowed for a smaller size ACU that
now provides more options for panel mounting.

2.3 ROUTING OF CABLES

Care must be taken not to bundle the MD41-( ) logic and low level signal lines with
any high energy sources. Examples of these sources include 400 HZ AC, Comm,
DME, HF and transponder transmitter coax. Always use shielded wire when shown
on the installation print.
Avoid sharp bends in cabling and routing near aircraft control cables.

REV. C 7 April 24, 2007

SECTION 3: INSTALLATION PROCEDURES

3.1 GENERAL INFORMATION

This section contains interconnect diagrams, mounting dimensions and other
information pertaining to the installation of the MD41-( ). After installation of cabling
and before installation of the equipment, ensure that power is applied only to the pins
specified in the interconnect diagram.

3.2 UNPACKING AND INSPECTING EQUIPMENT

When unpacking equipment, make a visual inspection for evidence of damage
incurred during shipment. The following parts should be included:

1. MD41-1484W (14VDC) or MD41-1488W (28VDC) Horiz. Mount
MD41-1494W (14VDC) or MD41-1498W (28VDC) Vertical Mount

2. Installation kit P/N 9016480 consisting of the following items:
A. J1 Connector Kit (15 pin) MCI P/N 9016479
B. 2 ea mounting brackets MCI P/N 8018483
C. 4 ea 4-40x ½ pan Phillips screws MCI P/N 90-416-00011
D. 2 ea 4-40x 9/16 flat Phillips screws MCI P/N 90-418-10011
E. 1 ea panel cutout template MCI P/N 8018954

3. Installation Manual MCI P/N 9016478

3.3 MOUNTING THE MD41-( )

Plan a location in the aircraft for the MD41-( ) to be mounted as close to the pilot’s
field of view as possible. The preferable location is near the HSI/CDI that will be
displaying the GPS information. Avoid mounting close to heater vents or other high
heat sources. Allow a clearance of at least 3 inches from back of unit for plug
removal.

Use the dimensions shown in figure 3-3 to prepare opening and screw holes for the
ACU. A file template has been provided to use for these measurements and hole
cutout Carefully measure the locations for the screw holes and mark the drill locations
with a center punch. Drill all six holes. A steel template (P/N 8018954) is supplied to
aid in locating holes and cutting out the panel. The template may be mounted to the
instrument panel to allow a file to be used to complete the cutout area. The front plate
of the ACU has a recessed area on the back so a flat head screw is not absolutely
necessary. Attach the mounting brackets to the rear side of the instrument panel with
four 4-40x1/2 pan-head screws. Insert the ACU through the front of instrument panel
and fasten with two 4-40 x 9/16 flat-head screws.

REV. C 8 April 24, 2007

3.4 INSTALLATION LIMITATIONS

Wire the aircraft harness according to figure 3-3. Use at least 24 AWG wire for all
connections. Avoid sharp bends and routing cable near high-energy sources. Care
must be taken to tie the harness away from aircraft controls and cables. Normal
installation techniques should be applied. Also see equipment limitations, section

1.2.6.

REAR VIEW OF MATING CONNECTOR

Connector Pinout

Pin # Pin #

1 INTG Annun. 9 Reserved
2 WPT Annun. 10 Lamp Test
3 MSG Annun. 11 Reserved
4 TERM Annun. 12 Reserved
5 28 VDC Power 13 Reserved
6 APR Annun. 14 Reserved
7 VLOC Annun. 15 Ground
8 GPS Annun.

FIGURE 3-1 SCHEMATIC PINOUT, 15 PIN HIGH DENSITY D-SUB

REV. C 9 April 24, 2007

15-pin

High Density

D-Sub

2.392 MAX

0.150

0.150

0.750

0.375

0.150

2.150

2.450

0.750

MD41-1484W, MD41-1488W MD41-1494W, MD41-1498W

2.150

0.375

FIGURE 3-2 OUTLINE DRAWING

2.450

REV. C 10 April 24, 2007

FIGURE 3-3 INSTRUMENT PANEL MOUNTING

REV. C 11 April 24, 2007

M D 4 1 -( ) A CU

J1

1) REFER TO G A RM IN GN S 430 , 430W or GN S 530, 530W INST ALLA TION

P4001

GNS 430/430W

P5001

GNS 530/530W

AIRCRAFT PWR
POWER G ND
APR ANN
TERM AN N
WPT ANN
MSG ANN
VLOC ANN
GPS ANN
INT G A NN
LAMP TEST

1A

TO MD41-ACU
CIRCUIT BREAKER

NOTES:

MANUAL FOR ACTUAL INSTALLATION.

2) ALL WIRING SHA LL BE 24 A W G U NLE SS OT HE RWISE NOTE D.

3) MOMENTARY SW ITCH FOR TEST. (optional connection)

4) 14 VDC FOR MD 41-1484W /1494W . 28 VDC FO R M D41 -1488W /1498W .

FIGURE 3-4: WIRING DIAGRAM, MD41-1484W/1488W/1494W-1498W

For GARMIN GNS 430/430W/530/530W

REV. C 12 April 24, 2007

SECTION 4: POST INSTALLATION CHECKOUT

4.1 PRE INSTALLATION TESTS

With the MD41-( ) disconnected, turn on the avionics master switch and verify that
aircraft power is on pin 5. Using an ohmmeter, verify pin 15 is aircraft ground.

4.2 OPERATING INSTRUCTIONS

Turn off the avionics master switch and connect the mating connector to the rear of
the MD41-( ). Turn on the avionics master switch and the MD41-( ) should come on
with the following annunciations.

1. VLOC or GPS

2. MSG may be flashing depending on the status of the GPS receiver.

Annunciation brightness at the minimum dimming level may be adjusted by rotation of
the dimmer control located on the side of the MD41-( ) case. CW rotation lowers the
dimming level.

Refer to section 5 of the Garmin GNS 430/430W or GNS 530/530W installation
manual for testing of annunciations.

No periodic maintenance or calibration is necessary for continued airworthiness of
the MD41-( ).

REV. C 13 April 24, 2007

DO-160C Environmental Qualification Form

NOMENCLATURE: Annunciation Control Unit (ACU)
MODEL NUMBER: MD41-( ) Series TSO NUMBER: C129, Class A1
MANUFACTURERS SPECIFICATIONS:

Minimum Performance Specification 7015613
Test Data Specification (TDS) 161, dated 2/12/07

MANUFACTURER:
ADDRESS:

CONDITIONS SECTION

Temperature and Altitude
Survival Low Temperature
Operating Low Temperature

Temperature Variation 5.0 Equipment tested to Category B
Humidity 6.0 Equipment tested to Category A
Operational Shocks and Crash
Safety
Vibration 8.0 Equipment tested to Category M and N
Explosive Atmosphere 9.0 Equipment identified as category X, no test performed.
Waterproofness 10.0 Equipment identified as category X, no test performed.
Fluids Susceptibility 11.0 Equipment identified as category X, no test performed.
Sand and Dust 12.0 Equipment identified as category X, no test performed.
Fungus 13.0 Equipment identified as category X, no test performed.
Salt Fog 14.0 Equipment identified as category X, no test performed.
Magnetic Effect 15.0 Equipment tested to Category Z
Power Input 16.0 Equipment tested to Category B
Voltage Spike 17.0 Equipment tested to Category A
Audio Frequency Conducted
Susceptibility
Induced Signal Susceptibility 19.0 Equipment tested to Category A
Radio Frequency Susceptibility
(Radiated and Conducted)
Emission of Radio Frequency
Energy
Lightning Induced Transient
Susceptibility
Lightning Direct Effects 23.0 Equipment identified as category X, no test performed.
Icing 24.0 Equipment identified as category X, no test performed.

Mid-Continent Instrument Co., Inc.

DESCRIPTION OF TEST

4.0

4.5.2

4.5.2

7.0

18.0 Equipment tested to Category B

20.4

20.5

21.0 Equipment tested to Category Z

22.0 Equipment identified as category X, no test performed.

Equipment tested to Category A1F2

Equipment tested to Paragraph 7.2.1

Equipment tested to Category T

REV. C 14 April 24, 2007